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NACA 64_1-112 Airfoil Data

by: Kindred Grey

Publication date: 2021-08-04

Usage: Attribution 4.0 International

Topics: Aerodynamics and Aircraft Performance, aircraft performance

Collection: kindredgreyarchive; additional_collections

Language: English

Item Size: 3.3M

This image is part of a series that was created for an open textbook, Aerodynamics and Aircraft Performance. The textbook is available here.

Preferred citation:

Kindred Grey (2021). "NACA 64_1-112 Airfoil Data." CC BY 4.0. Adapted from NACA. Public domain.

Alternative text:

(a) Lift curve slopes are shown for Reynolds numbers of 3.0, 6.0, and 9.0 times 10 to the 6. The curves are linear between angles of attack, alpha knot, of negative 14 and 14 degrees, with stall resulting in curves back towards 0 past these values and a y-intercept of 0.1. The lower end of the lines stop within the linear portion for all but the 6.0 times 10 ^6 case. An additional case at 6.0 times 10^6 is shown with standard roughness, which follows the same linear path until alpha knot of 10, after which it turns down slightly before the other cases. A final two cases are also shown with a 0.2 times c length flap deflected by 60 degrees, which results in the curve being shifted upward to a new y-intercept of approximately 1.4 c sub l, and the linear portion shifted to be between alpha knots of negative 14 and 6 to 10 degrees, for when standard roughness is or is not applied, respectively. The moment coefficients for the standard airfoils slowly decay across the linear portions from 0.05 to negative 0.025, with the moments corresponding to the two cases with flap deflection following similar shapes, but now between moment coefficient values of negative 0.15 and negative 0.225.

(b) Section drag coefficient, c sub d, is shown as a function of section lift coefficient, c sub l. The curves follow a roughly parabolic shapes, but now with an additional trough between the c sub l values of negative 0.1 and 0.3, centered around c sub l of 0.1 and c sub d of 0.004 to 0.005 as the Reynolds number decreases. The standard roughness curve is shifted up to a c sub d of 0.095, and loses the trough present in the earlier cases. The moment coefficients are all approximately negative 0.025 for all Reynolds numbers. The a c positions for Reynolds numbers of 3, 6, and 9 times 10 to the 6 are shown to be x over c of 0.265, 0.265, and 0.267, respectively, while the y over c positions are negative 0.013, negative 0.017, and negative 0.039, respectively.